CN116291895B - Missile fuel system capable of meeting high altitude use and design method thereof - Google Patents
Missile fuel system capable of meeting high altitude use and design method thereof Download PDFInfo
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- CN116291895B CN116291895B CN202310566370.0A CN202310566370A CN116291895B CN 116291895 B CN116291895 B CN 116291895B CN 202310566370 A CN202310566370 A CN 202310566370A CN 116291895 B CN116291895 B CN 116291895B
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- pump
- electric booster
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- 239000000446 fuel Substances 0.000 title claims abstract description 71
- 238000000034 method Methods 0.000 title claims abstract description 18
- 239000003921 oil Substances 0.000 claims abstract description 98
- 239000002828 fuel tank Substances 0.000 claims abstract description 19
- 238000005086 pumping Methods 0.000 claims abstract description 14
- 239000000295 fuel oil Substances 0.000 claims abstract description 10
- 238000010992 reflux Methods 0.000 claims abstract description 4
- 229920006395 saturated elastomer Polymers 0.000 claims description 18
- 238000004364 calculation method Methods 0.000 claims description 12
- 239000007788 liquid Substances 0.000 claims description 10
- 238000004088 simulation Methods 0.000 claims description 5
- 239000003350 kerosene Substances 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/236—Fuel delivery systems comprising two or more pumps
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/18—Network design, e.g. design based on topological or interconnect aspects of utility systems, piping, heating ventilation air conditioning [HVAC] or cabling
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/14—Pipes
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The invention discloses a missile fuel system capable of meeting the high altitude use and a design method thereof, belonging to the technical field of fuel systems, wherein the missile fuel system comprises an oil tank, a vent valve, an electric booster pump, a first pressure signal device, an electric gear pump, a second pressure signal device, an engine, a pump oil inlet pipeline, an exhaust pipeline, an oil pumping pipeline and an oil outlet pipeline; the electric booster pump is used for refluxing air in the fuel oil to the fuel tank under the full-flow working condition; the air plug generated at the inlet of the electric booster pump is prevented, the high altitude pressure drop of the fuel system is prevented, the fuel system can meet the high altitude performance of various limit heights, and the effective load, the range, the limit elevation and the reliability of the fuel system are improved.
Description
Technical Field
The invention belongs to the technical field of fuel systems, and particularly relates to a missile fuel system capable of meeting high altitude use and a design method thereof.
Background
The fuel system of the aircraft stores fuel and ensures that the fuel can be continuously supplied to the engine according to the pressure and the flow required by the engine under any specified state (such as various flying heights and flying attitudes). Large and medium-sized aircraft fuel systems and the complexity thereof, such as a conveyor, a fighter plane, a helicopter and the like, comprise a refueling system, a fuel discharging system, an explosion suppression system, a ventilation and pressurization system, a fuel supply and transportation system, a heat exchange system, a fuel management system and the like.
The missile fuel system is different from an aircraft fuel system in consideration of factors such as disposable use, short single time, cost and the like, and has the characteristics of simple system architecture, electric drive as a core, fewer components and the like. The architecture and calculation of the existing aircraft fuel system are relatively complex: for example, a light aircraft fuel system CN212079467U discloses a light aircraft fuel system, which comprises a fuel tank outlet pipe, a fuel tank return pipe, a fuel selection valve and a fuel pressure sensor connecting oil pipe. For example, an aircraft fuel system design method CN106446325B calculates the temperature field distribution of the fuel tank under the cold and hot limit temperature change of the aircraft by establishing an aircraft fuel supply system model, and obtains a method for meeting the requirement of fuel entering an engine inlet. An aircraft fuel system CN105438484a, a new fuel system is provided, which comprises a fuel tank, an engine oil supply pipeline, a pressure oil supply pipeline, a fuel tank output pipeline and a fuel supply main pipeline, wherein adjustable throttle valves and pressure sensors are arranged on the pressure oil supply pipeline and the fuel tank output pipeline, and when the aircraft engine is supplied with fuel, the fuel flow of a left wing fuel tank group, a right wing fuel tank group or a front fuselage fuel tank group and a rear fuselage fuel tank group can be simultaneously adjusted, so that the gravity center position of the aircraft is ensured to be unchanged. The prior aircraft fuel system patent technology cannot be directly used for missile fuel systems with novel all-electric configurations.
The missile flies at high altitude, when the atmospheric pressure is lower than the saturated steam pressure of the fuel, the air dissolved in the fuel is separated out, the liquid fuel can become the oil steam, the phenomenon is called cavitation, and the faults of oil pipeline cutoff, engine stopping and the like can occur in severe cases. Different technologies are adopted for cavitation in the current aerospace and aviation fields. If the high-pressure rubber air bag scheme is adopted in the aerospace field, along with the reduction of atmospheric pressure, the pressure relief valve is opened and then releases inert gas to ensure that the pressure of the oil tank is always higher than the saturated steam pressure of fuel oil, and the problems of large volume of the oil tank, complex structure, multiple accessories, heavy weight, easy failure of the pressure relief valve, high cost and the like exist in the mode. And for example, the air entraining and pressurizing technology of the engine is adopted in the aviation field, and the pressure of the oil tank is always higher than the saturated steam pressure of the fuel oil, but the problems of complex structure, multiple accessories, heavy weight, very high cost and the like are also solved.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the missile fuel system capable of meeting the requirement of high altitude use and the design method thereof, which can prevent the fuel system from falling off from the high altitude and can meet the high altitude performance of various limit heights.
In order to achieve the aim of the invention, the invention adopts the following technical scheme:
the missile fuel system capable of meeting the high altitude use comprises an oil tank, an electric booster pump and an engine;
the oil tank is provided with a vent valve;
a pump oil inlet pipeline and an exhaust pipeline are arranged between the oil tank and the electric booster pump;
the inlet of the electric booster pump is communicated with the oil tank through a pump oil inlet pipeline; the electric booster pump is provided with an exhaust hole, an exhaust pipeline is communicated with the exhaust hole, and the electric booster pump is used for refluxing air in the fuel oil to the fuel tank under the full-flow working condition;
an electric gear pump is arranged between the electric booster pump and the engine, and an inlet of the electric gear pump is communicated with an outlet of the electric booster pump through an oil pumping pipeline;
the outlet of the electric gear pump is communicated with the engine through an oil outlet pipeline;
a first pressure annunciator for collecting the outlet pressure of the electric gear pump is arranged on the pump oil outlet pipeline;
and a second pressure annunciator for collecting the outlet pressure of the electric gear pump is arranged on the oil outlet pipeline.
The basic principle of the missile fuel system capable of meeting the high altitude use in the invention is as follows: the exhaust hole is formed in the electric booster pump shell of the fuel system, the electric booster pump is connected with the fuel tank through the exhaust pipeline, so that air in fuel oil is returned to the fuel tank under the full-flow working condition, an inlet of the electric booster pump is prevented from generating air lock, the fuel system is prevented from falling off from high altitude, and the fuel system can meet the high altitude performance of various limit heights.
The invention also provides a design method of the missile fuel system capable of meeting the high altitude use, which comprises the following steps:
step 1: establishing a primary model of a missile fuel system;
step 2: according to the requirements of the engine on flow, pressure and vapor-liquid ratio, establishing the requirement parameters of an electric booster pump, an electric gear pump, an oil tank and a vent valve;
step 3: according to the demand parameters of the electric booster pump and the electric gear pump, designing the pipe diameters, the lengths and the pipe arrangement modes of the oil inlet pipeline, the oil outlet pipeline and the oil outlet pipeline of the pump;
step 4: designing and simulating internal flow fields of an electric booster pump and an electric gear pump to obtain flow, pressure, power and efficiency curves of the electric booster pump and the electric gear pump;
step 5: according to the flight profile of the missile under the extreme high altitude condition, an exhaust pipeline is designed between the outlet of the electric booster pump and the oil tank, and whether the flow in the exhaust pipeline meets the required exhaust flow of gas-liquid mixed transportation is checked in a simulation mode; if yes, determining the pipe diameter and the length of an exhaust pipeline; if not, adjusting the pipe diameter and the length of the exhaust pipeline, and repeating the step 5 until the flow in the exhaust pipeline meets the required gas-liquid mixed delivery exhaust flow;
step 6: according to a pressure loss calculation formula, calculating the pressure loss from the oil tank to the inlet of the engine, and judging whether the electric booster pump and the electric gear pump meet the boosting index; if yes, determining a preliminary model of the fuel system; if not, repeating the steps 2 to 5 until the preliminary model of the fuel system is determined.
Further, in step 4, when designing the electric booster pump, the rated flow of the electric booster pump needs to be increased to 120% by adopting an increasing flow design method so as to meet the flow required by the exhaust pipeline;
the supercharging pressure of the electric booster pump at the design flow point of 120% is larger than the inlet saturated vapor pressure of the electric gear pump under extreme conditions; the calculation formula of the inlet saturated vapor pressure of the electric gear pump is as follows
wherein ,P2 The saturated vapor pressure of the inlet of the electric gear pump is measured as kPa, the delta P is the supercharging pressure of the electric booster pump, and the unit is kPa; pv is the saturated vapor pressure of aviation kerosene, the unit is kPa, 10-20 is the safety allowance, and the unit is kPa.
Further, in step 4, an exhaust nozzle is arranged in the exhaust hole on the electric booster pump, and the exhaust nozzle is fixedly connected with an exhaust pipeline; the diameter of the exhaust joint is 1/3 or 1/4 of the pipe diameter of the exhaust pipeline.
Further, in step 6, the pressure loss calculation formula is:
wherein ,the pressure loss of the oil inlet pipeline of the pump; />Pressure loss for the pump-out tubing; />The pressure loss of the oil outlet pipeline; />Flow resistance for the electric booster pump; />、/>、/>The lengths of the oil inlet pipeline, the oil outlet pipeline and the oil outlet pipeline are respectively; />、/>、/>The pipe diameters of the oil inlet pipeline, the oil outlet pipeline and the oil outlet pipeline are respectively; />、/>、/>The flow rates of the oil inlet pipeline, the oil outlet pipeline and the oil outlet pipeline are respectively; the pressure loss of the exhaust pipeline is not required to be considered; />For the resistance coefficient along the way>Is a local drag coefficient.
The beneficial effects of the invention are as follows: a missile fuel system capable of meeting high altitude use and a design method thereof are provided, an exhaust hole is arranged on an electric booster pump shell of the fuel system, and the electric booster pump is connected with an oil tank through an exhaust pipeline, so that air in fuel oil under a full-flow working condition is returned to the oil tank, an inlet of the electric booster pump is prevented from generating air lock, the fuel system is prevented from being compressed at high altitude, the fuel system can meet high altitude performances of various limit heights, and the effective load, range, limit elevation height and reliability of the fuel system are improved.
Drawings
FIG. 1 is a schematic diagram of a missile fuel system capable of meeting the high altitude use in the present invention;
FIG. 2 is a flow chart of a method of designing a missile fuel system that can be used at high altitudes in accordance with the present invention;
FIG. 3 is a schematic diagram of a simulated internal flow field of an electric booster pump;
FIG. 4 is a graph of an increased flow design of an electric booster pump;
FIG. 5 is a graph comparing simulated boost and actual boost for an electric gear pump at different flows.
1, an oil tank; 2. a vent valve; 3. an electric booster pump; 4. a first pressure annunciator; 5. an electric gear pump; 6. a second pressure annunciator; 7. an engine; 8. a pump oil inlet pipeline; 9. an exhaust line; 10. an oil pump-out pipeline; 11. and an oil outlet pipeline.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and all the inventions which make use of the inventive concept are protected by the spirit and scope of the present invention as defined and defined in the appended claims to those skilled in the art.
As shown in fig. 1, the invention provides a missile fuel system capable of meeting high altitude use, which comprises a fuel tank 1, an electric booster pump 3 and an engine 7; the oil tank 1 is provided with a vent valve 2; a pump oil inlet pipeline 8 and an exhaust pipeline 9 are arranged between the oil tank 1 and the electric booster pump 3; the inlet of the electric booster pump 3 is communicated with the oil tank 1 through a pump oil inlet pipeline 8; the electric booster pump 3 is provided with an exhaust hole, and specifically, an exhaust connector is arranged in the exhaust hole of the electric booster pump 3 and fixedly connected with an exhaust pipeline 9; the diameter of the exhaust joint is 1/3 or 1/4 of the pipe diameter of the exhaust pipeline 9. The electric booster pump 3 is used for refluxing air in the fuel oil to the fuel tank 1 under the full flow condition.
An electric gear pump 5 is arranged between the electric booster pump 3 and the engine 7, and the inlet of the electric gear pump 5 is communicated with the outlet of the electric booster pump 3 through an oil pumping pipeline 10. The oil pumping pipeline 10 is provided with a first pressure annunciator 4 for collecting the outlet pressure of the electric gear pump 5; the oil outlet pipeline 11 is provided with a second pressure annunciator 6 for collecting the outlet pressure of the electric gear pump 5.
According to the missile fuel system capable of meeting high altitude use, the exhaust holes are formed in the shell of the electric booster pump 3 of the fuel system, and the electric booster pump 3 is connected with the fuel tank 1 through the exhaust pipeline 9, so that air in fuel oil is returned to the fuel tank 1 under a full-flow working condition, air lock generated at an inlet of the electric booster pump 3 is prevented, high altitude pressure drop of the fuel system is prevented, and the fuel system can meet high altitude performances of various limit heights.
As shown in FIG. 2, the invention also provides a design method of the missile fuel system capable of meeting the high altitude use, which comprises the following steps:
step 1: establishing a primary model of a missile fuel system;
step 2: according to the requirements of the engine 7 on flow, pressure and vapor-liquid ratio, establishing the requirement parameters of the electric booster pump 3, the electric gear pump 5, the oil tank 1 and the vent valve 2;
step 3: according to the demand parameters of the electric booster pump 3 and the electric gear pump 5, the pipe diameters, the lengths and the pipe arrangement modes of the oil pumping pipeline 8, the oil pumping pipeline 10 and the oil outlet pipeline 11 are designed;
step 4: designing and simulating internal flow fields of the electric booster pump 3 and the electric gear pump 5 to obtain flow, pressure, power and efficiency curves of the electric booster pump 3 and the electric gear pump 5;
step 5: according to the flight profile of the missile under the extreme high altitude condition, an exhaust pipeline 9 is designed between the outlet of the electric booster pump 3 and the oil tank 1, and whether the flow in the exhaust pipeline 9 meets the required exhaust flow of gas-liquid mixing transportation is checked in a simulation mode; if yes, determining the pipe diameter and the length of the exhaust pipeline 9; if not, adjusting the pipe diameter and the length of the exhaust pipeline 9, and repeating the step 5 until the flow in the exhaust pipeline 9 meets the required exhaust flow of the gas-liquid mixing transportation;
step 6: according to a pressure loss calculation formula, calculating the pressure loss from the oil tank 1 to the inlet of the engine 7, and judging whether the electric booster pump 3 and the electric gear pump 5 meet the supercharging index; if yes, determining a preliminary model of the fuel system; if not, repeating the steps 2 to 5 until the preliminary model of the fuel system is determined.
Further, in step 4, as shown in fig. 4, when the electric booster pump 3 is designed, the rated flow of the electric booster pump 3 is increased to 120% by adopting an increasing flow design method, so as to meet the flow required by the exhaust pipeline 9;
specifically, in fig. 4, a curve a is represented as an original curve, a curve B is represented as a curve designed to increase the flow rate, and Δpd is a rated boost pressure, and Qd is a rated flow rate. The supercharging pressure of the electric booster pump 3 at the design flow point of 120% is larger than the inlet saturated vapor pressure of the electric gear pump 5 under extreme conditions; the calculation formula of the saturated vapor pressure at the inlet of the electric gear pump 5 is as follows
wherein ,P2 The saturated vapor pressure of the inlet of the electric gear pump 5 is measured in kPa, the delta P is the pressure of the electric booster pump 3, and the unit is kPa; pv is the saturated vapor pressure of aviation kerosene, the unit is kPa, 10-20 is the safety allowance, and the unit is kPa.
Further, in step 6, the pressure loss calculation formula is:
wherein ,the pressure loss of the oil inlet pipeline 8 of the pump; />Pressure loss for the pump-out line 10; />A pressure loss for the oil outlet line 11; />A flow resistance for the electric booster pump 3; />、/>、/>The lengths of the oil pumping pipeline 8, the oil pumping pipeline 10 and the oil outlet pipeline 11 are respectively; />、/>、/>The pipe diameters of the oil pumping pipeline 8, the oil pumping pipeline 10 and the oil outlet pipeline 11 are respectively; />、/>、/>The flow rates of the oil pumping pipeline 8, the oil pumping pipeline 10 and the oil outlet pipeline 11 are respectively; the pressure loss of the exhaust line 9 does not need to be considered; />For the resistance coefficient along the way>Is a local drag coefficient.
In the embodiment, the inlet flow rate of the engine 7 is 100L/h, the inlet pressure is 0.037-0.35 MPa, and the highest flying height is 15000m. The electric gear pump 5 is used for pressurizing 0.3MPa, the electric booster pump 3 is used for pressurizing 0.03-0.06 MPa, and the power supply is 28VDC.
Through a calculation formula of the saturated vapor pressure at the inlet of the electric gear pump 5,the inlet saturated vapor pressure of the electric gear pump 5 is far greater than the saturated vapor pressure of the fuel (0.0425 MPa) and meets the inlet pressure requirement of the gear pump.
According to the electric gear pump 5, the pressure is increased by 0.3MPa, the pressure is increased by 0.03-0.06 MPa, and the oil inlet pipeline with the pipe diameter of 8mm and the pipeline length of 100mm are obtained. Fig. 3 and 5 are obtained according to simulation, and design requirements are met.
A schematic diagram of the internal pressure distribution of the electric booster pump under three conditions of 20L/H, 60L/H and 120L/H is obtained in FIG. 3.
In fig. 5, the simulation Δp is the simulated electric booster pump 3 boost, and the Test Δp is the actual measured electric booster pump 3 boost, which can be obtained directly by the first pressure signal 4; the formulationηThe supercharging efficiency of the simulated electric booster pump 3; test (Test)ηTo actually measure the supercharging efficiency of the electric booster pump 3.
According to the steps 5 to 6,=8kPa，/>=1kPa，
=5kPa，/>=2kPa。
according to the calculation, when the electric booster pump 3 does not work, the pressure loss of the fuel oil pipeline is 0.008kPa, the engine 7 can work normally, the high altitude performance of various limit heights is met, and the effective load, the range, the limit elevation and the reliability of the electric booster pump are improved.
Claims (3)
1. A design method of a missile fuel system capable of meeting the high altitude use is characterized in that the missile fuel system comprises an oil tank, an electric booster pump and an engine;
a vent valve is arranged on the oil tank;
a pump oil inlet pipeline and an exhaust pipeline are arranged between the oil tank and the electric booster pump;
the inlet of the electric booster pump is communicated with the oil tank through the pump oil inlet pipeline; the electric booster pump is provided with an exhaust hole, the exhaust pipeline is communicated with the exhaust hole, and the electric booster pump is used for refluxing air in the fuel oil to the fuel tank under the full-flow working condition;
an electric gear pump is arranged between the electric booster pump and the engine, and an inlet of the electric gear pump is communicated with an outlet of the electric booster pump through an oil pumping pipeline;
the outlet of the electric gear pump is communicated with the engine through an oil outlet pipeline;
a first pressure annunciator for collecting the outlet pressure of the electric gear pump is arranged on the oil pumping pipeline;
the oil outlet pipeline is provided with a second pressure annunciator for collecting the outlet pressure of the electric gear pump;
the design method comprises the following steps:
step 1: establishing a primary model of a missile fuel system;
step 2: according to the requirements of the engine on flow, pressure and vapor-liquid ratio, establishing the requirement parameters of an electric booster pump, an electric gear pump, an oil tank and a vent valve;
step 3: according to the demand parameters of the electric booster pump and the electric gear pump, designing the pipe diameters, the lengths and the pipe arrangement modes of the oil inlet pipeline, the oil outlet pipeline and the oil outlet pipeline of the pump;
step 4: designing and simulating internal flow fields of an electric booster pump and an electric gear pump to obtain flow, pressure, power and efficiency curves of the electric booster pump and the electric gear pump; in the step 4, when the electric booster pump is designed, the design method of increasing the flow is adopted, and the rated flow of the electric booster pump needs to be increased to 120 percent so as to meet the flow required by an exhaust pipeline;
the supercharging pressure of the electric booster pump at the design flow point of 120% is larger than the inlet saturated vapor pressure of the electric gear pump under extreme conditions; the calculation formula of the inlet saturated vapor pressure of the electric gear pump is as follows
wherein ,P2 The saturated vapor pressure of the inlet of the electric gear pump is measured as kPa, the delta P is the supercharging pressure of the electric booster pump, and the unit is kPa; pv is saturated vapor pressure of aviation kerosene, the unit is kPa, 10-20 is safety allowance, and the unit is kPa;
step 5: according to the flight profile of the missile under the extreme high altitude condition, an exhaust pipeline is designed between the outlet of the electric booster pump and the oil tank, and whether the flow in the exhaust pipeline meets the required exhaust flow of gas-liquid mixed transportation is checked in a simulation mode; if yes, determining the pipe diameter and the length of an exhaust pipeline; if not, adjusting the pipe diameter and the length of the exhaust pipeline, and repeating the step 5 until the flow in the exhaust pipeline meets the required gas-liquid mixed delivery exhaust flow;
step 6: according to a pressure loss calculation formula, calculating the pressure loss from the oil tank to the inlet of the engine, and judging whether the electric booster pump and the electric gear pump meet the boosting index; if yes, determining a preliminary model of the fuel system; if not, repeating the step 2 to the step 5 until a preliminary model of the fuel system is determined.
2. The method for designing missile fuel system capable of being used in high altitude as claimed in claim 1, wherein in step 4, an exhaust nozzle is provided in the exhaust hole of the electric booster pump, and the exhaust nozzle is fixedly connected with the exhaust pipeline; the diameter of the exhaust joint is 1/3 or 1/4 of the pipe diameter of the exhaust pipeline.
3. The method of claim 1, wherein in step 6, the pressure loss calculation formula is:
wherein ,the pressure loss of the oil inlet pipeline of the pump; />Pressure loss for the pump-out tubing; />The pressure loss of the oil outlet pipeline; />Flow resistance for the electric booster pump; />、/>、/>The lengths of the oil inlet pipeline, the oil outlet pipeline and the oil outlet pipeline are respectively; />、/>、/>The pipe diameters of the oil inlet pipeline, the oil outlet pipeline and the oil outlet pipeline are respectively; />、/>、/>The flow rates of the oil inlet pipeline, the oil outlet pipeline and the oil outlet pipeline are respectively; the pressure loss of the exhaust pipeline is not considered; />For the resistance coefficient along the way>Is a local drag coefficient.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310566370.0A CN116291895B (en) | 2023-05-19 | 2023-05-19 | Missile fuel system capable of meeting high altitude use and design method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310566370.0A CN116291895B (en) | 2023-05-19 | 2023-05-19 | Missile fuel system capable of meeting high altitude use and design method thereof |
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| CN116291895A CN116291895A (en) | 2023-06-23 |
| CN116291895B true CN116291895B (en) | 2023-10-24 |
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| CN117622496A (en) * | 2024-01-23 | 2024-03-01 | 西安爱生技术集团有限公司 | Unmanned aerial vehicle fuel system suitable for electric control engine and design method |
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